| 摘要 |
PROBLEM TO BE SOLVED: To improve efficiency over the whole of a supersonic aircraft propulsion system by improving acceleration performance when soaring at a transonic speed, increasing/decreasing the number of rotation of a fan with fixed thrust in supersonic cruise, and controlling the intake back pressure to reduce a bleed air flow in an intake. SOLUTION: The inlet area of a high-pressure turbine (HPT) and a low-pressure turbine (LPT) are fixed, and the outlet area of the both are variable. In transonic cruise, the thrust for acceleration is increased by widening the outlet area of the HPT, and bleeding air through an inlet of the LPT to raise the number of revolution of a compressor (HPC) without excessively rotating a fan. In supersonic cruise, the number of rotation of the fan is changed at a nearly constant number of revolution of the HPC by maintaining high thrust with the bleed air of the inlet of the LPT, and while opening/closing the outlet area of the LPT (the outlet area of a core duct) to change a LPT expansion ratio. COPYRIGHT: (C)2011,JPO&INPIT
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